Spacecraft aerodynamics and trajectory simulation during aerobraking

Abstract：This paper uses a direct simulation Monte Carlo(DSMC)approach to simulate rarefied aerodynamic characteristics during the aerobraking process of the NASA Mars Global Surveyor(MGS)spacecraft.The research focuses on the flowfield and aerodynamic characteristics distribution under various free stream densities.The variation regularity of aerodynamic coefficients is analyzed.The paper also develops an aerodynamics-aeroheating-trajectory integrative simulation model to preliminarily calculate the aerobraking orbit transfer by combining the DSMC technique and the classical kinematics theory.The results show that the effect of the planetary atmospheric density,the spacecraft yaw,and the pitch attitudes on the spacecraft aerodynamics is significant.The numerical results are in good agreement with the existing results reported in the literature.The aerodynamics-aeroheating-trajectory integrative simulation model can simulate the orbit tran,sfer in the complete aerobraking mission.The current results of the spacecraft trajectory show that the aerobraking maneuvers have good performance of attitude control. 作者： Author： Wen-pu ZHANG  Bo HAN  Cheng-yi ZHANG 作者單位： Institute of Fluid Engineering,School of Aeronautics and Astronautics,Zhejiang University,Hangzhou 310027,P.R.China 期 刊： 應用數學和力學（英文版）   EISCI Journal： APPLIED MATHEMATICS AND MECHANICS 年，卷(期)： 2010, 31(9) 分類號： V411.4 V412.41 Keywords： aerobraking    rarefied gas dynamics    direct simulation Monte Carlo(DSMC)    Mars spacecraft    aerodynamic characteristic    trajectory simulation    機標分類號： TM V1 機標關鍵詞： during    aerodynamic characteristics    simulation model    direct simulation Monte Carlo    numerical results    atmospheric density    orbit transfer    performance    paper    kinematics    agreement    research    DSMC    approach    focuses    stream    Mars    MGS 基金項目： Project supported by the Aerospace Foundation of China Academy of Space Technology

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